48results about How to "High storage rate" patented technology

The invention relates to truss type foldable units and foldable supporting arms formed by the same and particularly to an elastic hinge driving truss type foldable unit and a foldable supporting arm. The elastic hinge driving truss type foldable unit and the foldable supporting arm aim at solving the problems that the existing hinged supporting arm is complicated in driving mechanism, large in folding size and low in repeated unfolding accuracy and accordingly the structural weight is greatly increased and the unfolding reliability is low. The elastic hinge driving truss type foldable unit comprises an upper frame, a lower frame, N elastic hinge type folding arms and N groups of drawing cable assemblies; the upper frame and the lower frame are arranged in a parallel mode; N vertexes of the upper frame and N vertexes of the lower frame are arranged in an upper and lower corresponding mode; every two corresponding vertex angles formed between the upper frame and the lower frame are supported through the corresponding elastic hinge type folding arm and can be connected with each other in a rotating mode; every group of drawing cable assembly is arranged at the diagonal position in a rectangular plane which is formed by the upper frame, the lower frame and the two corresponding adjacent elastic hinge type folding arms. The elastic hinge driving truss type foldable unit and the foldable supporting arm are applied to a satellite, a space station and a space probe.

The invention discloses a device that can stretch the reflection plane in space, which includes a foldable ring pole, a foldable rib pole and a plurality of connection joints, wherein, every two foldable ring poles (1) are connected by a ring pole connection joint (2) to form a furling and stretching ring structure; every two foldable rib poles (3) form a furling and stretching rib structure by a rib pole connection joint (4); one end of the rib structure is connected with the ring structure by a ring rib connection joint (5) and the other end is connected with a central ribbed tube connection joint (6) to form a whole rigid body; the ring pole connection joint and the rib pole connection joint drives, locks and controls the foldable ring pole to stretch from the vertical furled state to the horizontal stretched state and controls the foldable rib pole to stretch from the vertical furled state to the expected curve proximity state. The invention has low area density, high structural precision and large holding rate and can be used for the ground or space as a reflector or a collector.

The high-rigidity synchronously spreading folded space extension arm consists of folded truss units capable of being expanded repeatedly and being spread, driving system, power supply system and supporting space platform. The folded truss units are basic units to constitute the extension arm and are connected mutually via standard triangular joints; the driving system is inside the triangular space in the bottom of the extension arm and is connected to the supporting space platform and to the power supply system through the transmission shaft. The truss structure in triangular prism form of the present invention has geometrical stability, high structural rigidity and high unit repeatability, and may be spread and folded synchronously in high precision. The present invention may be used in large communication satellite, electronic reconnaissance satellite and space station platform.

The invention provides a double-layer annular truss antenna mechanism based on passive drive and relates to double-layer annular truss type expandable antenna mechanisms. The problems that an existing large-caliber single-ring annular truss antenna is small in rigidity, the use rigidity requirement can not be met, an existing annular truss antenna mechanism is complex in drive structure and large in weight, inhaul cables are prone to be twisted after being used for unfolding the mechanism, and the unfolding reliability is low are solved. The double-layer annular truss antenna mechanism comprises multiple inner and outer truss foldable unit modules, multiple inner transition folding assemblies and multiple outer transition folding assemblies. Each inner and outer truss foldable unit module comprises an inner folding unit module, an outer folding unit module and two inner and outer connection truss assemblies. Inner supporting vertical rods and outer supporting vertical rods which are opposite are connected through the inner and outer connection truss assemblies. After the inner and outer truss foldable unit modules are unfolded, an inner and outer double-layer annular truss polyhedron is formed. The double-layer annular truss antenna mechanism is used for a satellite, a space station and a space probe.

The invention discloses a satellite-borne solid-surface deployable antenna which is composed of a solid-surface reflector, a deployable mechanism and a driving component. The deployable mechanism is composed of multiple synchronous three-bar deployable units and synchronous two-bar deployable units combined in an array. The solid-surface reflector is composed of a plurality of rigid sheets. The driving component includes a driving motor and an elastic energy storage element. The solid-surface reflector and the deployable mechanism are connected through a universal hinge. Under the action of the driving motor, the solid-surface reflector realizes first spatial synchronous deployment through the deployable mechanism. Under the action of the elastic energy storage element and a compression spring, the solid-surface reflector realizes second spatial synchronous deployment. After deployment, any two adjacent panels of the solid-surface reflector are hinged and locked by a locking mechanism,and the whole antenna is stabilized in a fully deployed state. The satellite-borne solid-surface deployable antenna has the characteristics of large deployment aperture, high deployment and support stiffness, and high precision of surface profile, and can be used as a reflector or a collector in space or on the ground.

The invention relates to a foldable structure, in particular to a space unfolding structure which can be unfolded without needing a driving device. The space unfolding structure comprises a cylinder, a heater, memory alloys and films. The heater is installed in the cylinder, a plurality of memory alloys are evenly distributed on the periphery of the cylinder in the circumferential direction, one end of every memory alloy penetrates through the cylinder and is connected with the heater, the other end of every memory alloy is a free end, the memory alloys are sleeved with the films in a stacked mode through the free ends of the memory alloys, the films are in sealed connection with the cylinder, the free ends of the memory alloys sleeved with the films are sequentially bent in the clockwise direction and coiled around the cylindrical surface of the cylinder, and an inflation nozzle capable of inflating the cylinder is installed on the cylinder. The space unfolding structure does not need to be driven by a motor, is simple in structure and easy to install and does not occupy too much space, and reliability of the space unfolding structure is greatly improved.

A cable-stayed stretch-draw annular expandable antenna mechanism relates to an expandable antenna mechanism and solves the problem that an existing annular truss mechanism has a decrease in stiffnesswith an increase in the diameter of an antenna, cannot meet the stiffness requirements and has a complicated driving mechanism, a large weight and low expansion reliability. The cable-stayed stretch-draw annular expandable antenna mechanism comprises a plurality of cable-stayed stretch-draw expandable unit modules. Each of the cable-stayed stretch-draw expandable unit modules comprises a first expandable unit module and a second expandable unit module which are connected together. The plurality of first expandable unit module and the plurality of second expandable unit modules are arranged alternately and connected together to form a cable-stayed stretch-draw annular truss after expanded. The cable-stayed stretch-draw annular expandable antenna mechanism is good in reliability, compact instructure, light in weight, easy to drive, high in stiffness after fully expanded, meets the requirements for a large-diameter antenna, and is applied to a communication satellite, a space station anda space detector.

The invention relates to the technical field of architectural engineering and aerospace, and aims to provide an unfoldable dome structure of a tension spring-driven shear hinge. The structure comprises at least three annular units, wherein rod members and node parts are connected in a hinged manner; low table parts of every two rod members are relatively assembled by screws to form shear hinge structures; six shear hinge structures are arranged in sequence, and are connected by twelve node parts to form one annular unit; the node parts at the external in one shear hinge structure are connected with the node parts at the same side at the internal through tension springs; the gathering state size of the structure depends on the section sizes and the length sizes of the rod members, and the spreading state size of the structure depends on the length sizes of the rod members, so that the gathering rate is higher, the small space requirement in rocket launching and the large space requirement in aerospace are satisfied, and the assembly, construction and transportation convenience requirements and the building space coverage requirement are satisfied; and the structure is convenient to be carried in the folding state, and is wide in functions in the spreading state. The structure is wide in application range, is gradient, and is higher in economic effect.

The invention relates to a solar power station having battery panels capable of performing multi-degree-freedom movement, relating to the solar generating case. The invention solves the problems that the solar battery panels of the current solar generating vehicle are poor in flexibility and solar energy utilization rate is low. The solar power station having battery panels capable of performing multi-degree-freedom movement comprises a master base, a lifting mechanism, a revolution mechanism, a tilting mechanism, an upper truss, a plurality of side trusses, a plurality of execution mechanisms and a plurality of solar battery panels. The lifting mechanism, the revolution mechanism, the tilting mechanism, and the upper truss are arranged on the master base; the plurality of side trusses are arranged on the circumference of the upper truss; each side truss is hinged with the upper truss; the top surface of each side truss and the top surface of the upper truss are provided with solar battery panels; and the solar battery panel of each side truss is connected to the solar battery panel on the top surface of the upper truss through the execution mechanism. The invention is easy to use and the effective area for absorbing the solar energy is big. Meanwhile, the invention also has functions of tilting, revolution and lifting, and improves the flexibility. The invention is used for solar power generating.

The invention discloses a damping component of a large self-unfolding satellite antenna, and aims to solve a problem of profile precision errors caused by vibration in an unfolding process of an existing unfolding antenna mechanism and in a posture adjusting process after unfolding. The component comprises a multi-finger-petal friction damper, a self-resetting elastic support friction damper, an elastic driving hinge and a satellite structure rod piece. The multi-finger-petal friction damper controls transverse vibration of the satellite unfolding antenna and comprises a multi-finger-petal rodwhich is pressed on a structural rod piece through an adjustable pressing ring. The self-resetting elastic support friction damper controls axial vibration and comprises a metal rubber, a guide rod,an SMA pull wire and an outer sleeve. The elastic driving hinge provides unfolding power through a volute spring, and an unfolding speed and synchronism are controlled through a gear. The satellite structure rod piece is fixedly connected with other assemblies so that integrity of the unfolded antenna is ensured. The component is used for satellites and space detectors.

The embodiment of the invention provides a deployable rigid reflector antenna. The antenna comprises a support base assembly 1, a central fixing panel assembly 2 and a deployable panel assembly 3. Thesupport base assembly 1 and the central fixing panel assembly 2 are fixedly connected. The support base assembly 1 is fixedly connected with the deployable panel assembly 3 through the rotating shaftassembling components 1-5 of the support base assembly 1. When the rotating shaft assembling components 1-5 rotate, the deployable panel assembly 3 is driven to deploy so that the central fixing panel assembly 2 and the deployed deployable panel assembly 3 form a complete antenna reflector together. According to the deployable rigid reflector antenna, the deployable panel assembly is driven to rotate and deploy through the rotating shaft assembling components of the support base assembly so that the solid reflector antenna with large aperture, high accuracy, high rigidity and high storage rate can be realized.

The invention belongs to the field of industrial environmental protection, and particularly relates to industrial filter drum type dust removal equipment. The industrial filter drum type dust removal equipment comprises a machine body, filter elements, a dust bin, first air bags, fixed covers, a motor, a screw rod, a moving nut, an air pocket, a polished rod, cage frames, a supporting seat, an exhaust module and supporting rings, wherein through holes are formed in the machine body; the first air bags are fixed on the through holes; the supporting seat is mounted on the first air bags; through holes are formed in the supporting seat; the left ends of the cage frames are placed in the through holes; the fixed covers are located at the left end of the supporting seat; the filter elements are mounted on the cage frames; the screw rod is connected with the machine body through a bearing; the motor is fixed on the machine body; the moving nut is mounted on the screw rod; the lower end of the polished rod is fixed on the machine body; the air pocket is fixed at the left end of the moving nut; the exhaust module is connected with the right end of the machine body; the dust bin is located below the machine body; a second air bag is arranged between the dust bin and the machine body; the second air bag can vibrate under the action of air flow and drive the dust bin to vibrate, so that the dust can be accumulated more tightly, and the dust collection rate is increased.

The invention relates to a novel high-storage-rate VHF antenna in the technical field of spaceflight satellite equipment. The novel high-storage-rate VHF antenna comprises a base, antenna radiation arms, a self-unfolding device and a supporting device. The self-unfolding device comprises elastic rods, the multiple elastic rods are connected to the base at intervals to form a barrel-shaped structure, the supporting device comprises a supporting ring, the supporting ring is connected with the elastic rods and located at the top of the barrel-shaped structure, the antenna radiation arm spirally surrounds the barrel-shaped structure, one end of the antenna radiation arm is connected with the base, and the other end of the antenna radiation arm is connected with the elastic rods or the supporting ring; the elastic rod deforms into a spiral shape to be wound around the surface of the base under the action of external force, and the elastic rod recovers to the original shape after the external force is relieved. The high storage rate of the VHF antenna is realized in a disc pressing manner, and the antenna is suitable for high-gain measurement and control communication antenna systems of different satellite platforms, is especially suitable for being carried by microsatellites, micro-nano satellites and other platforms with limited platforms, and has very high application and popularization values.

The invention discloses an anti-vibration self-resetting satellite antenna supporting rod structure, which comprises a self-resetting elastic support friction damping component for controlling axial vibration of an unfolding component, a volute spiral spring for providing unfolding driving force for an antenna supporting rod, a hinge and a carbon fiber rod for connecting all parts. The self-resetting elastic support friction damping structure control component has the same axis, a groove is formed in the inner cylinder baffle, the radial movement is limited through limiting screws, and the twosymmetrically-arranged hexagon socket head cap screws play a clamping role and are used for preventing axial movement of the inner cylinder baffle. The two metal rubber blocks playing a role in energy consumption are arranged between the inner cylinder and the outer cylinder and are symmetrically distributed on the two sides of the inner cylinder bafflee; one end of the inner cylinder is connected with the internal thread connecting piece which is connected with the carbon fiber rod; and the other ends of the outer cylinder and the inner cylinder are connected with external thread connectingpieces. When the inner cylinder and the outer cylinder generate relative motion due to vibration, axial vibration of the unfolding component is restrained through friction energy consumption of the metal rubber blocks.

The invention discloses a novel fixed-surface deployable antenna structure, and the structure is characterized in that the structure comprises a central disc base which has N sides which are arrangedto be a polygon; folding units which are circumferentially distributed in the circumferential direction of the central disc base, wherein the number of the folding units is N, and the folding units are hinged to each edge of the central disc base; each folding unit is composed of a first panel body, a second panel body and a third panel body, the first panel body and the second panel body intersect to form a first peak line, and the second panel body and the third panel body intersect to form a valley line; the first panel of one folding unit in two adjacent folding units is intersected with the third panel of the other folding unit to form a second peak line; and the extension lines of the first peak line, the valley line and the second peak line penetrate through the regular polygon corner of the central disc base. The fixed-surface deployable antenna structure has the advantages of simple integral device, light weight, high antenna storage rate, particularly high storage rate in theheight direction, simplicity in control and operation of the deploying process, capability of maintaining the deploying configuration of the antenna and the like.

The invention discloses a cement bag collection device for road construction. The device structurally comprises a handrail, a storage box, an inclined strut, a flat absorbing structure and a motor box. The inclined strut is obliquely installed on the flat absorbing structure, the handrail is fixed to the head end of the inclined strut, the flat absorbing structure is mechanically connected with the storage box on one side and also fixedly connected with the motor box on the top end face, the flat absorbing structure is provided with a motor, an inlet flat structure, a negative pressure structure, a roller transmission structure, a main body linkage structure, a pressure collection structure and a shell, one end of the shell is mechanically connected with the storage box, the other end of the shell is provided with the inlet flat structure, cement bags located on the surface of a road are sucked in through the negative pressure structure, redundant air in the cement bags is pressed awaythrough the inlet flat structure, the cement bags are transported to the pressure collection structure through the roller transmission structure and pressed and stacked together time and time again,readjustment is not needed, the cement bags can be directly taken out and bundles, bowing collection is avoided, and collection efficiency is improved.

The invention relates to the technical field of aviation and aims to provide a torsion spring driven moonlet borne expandable plane structure and a mounting method thereof. The torsion spring driven moonlet borne expandable plane structure comprises equilateral triangle unfolding units, wherein each equilateral triangle unfolding unit comprises a thin-walled rod member, a node, a connector, a torsion spring and a pin shaft; adjacent equilateral triangle unfolding units are spliced by using different nodes. The mounting method comprises the following steps of mounting effective load, connecting the thin-walled rod members with the connectors, connecting the thin-walled rod members with six-directional nodes, three-directional nodes, four-directional nodes, and center nodes, mounting two-directional nodes, welding a lead, connecting the moonlet borne expandable plane structure with a moonlet, and connecting a lead. The expandable plane structure is unfolded by the torsion springs at joints of the expandable plane structure and can be quickly switched into an unfolding state from a folding state, so that the expandable plane structure is simple in operation and high in expansion reliability.